Impingement structure for jet engine mid-rutbine frame

ABSTRACT

A mid-turbine frame (MTF”) for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine (“HPT”) and a low pressure turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

FIELD

The present disclosure relates to an impingement structure for a jetengine mid-turbine frame, and more particularly, to an impingementstructure, also referred to as a perforated structure, for a jet enginemid-turbine frame vane segment.

BACKGROUND

Gas turbine engines (e.g., jet engines) generally include a compressorto pressurize inflowing air, a combustor to burn a fuel in the presenceof the pressurized air, and a turbine to extract energy from theresulting combustion gases. The compressor may comprise a low pressurecompressor, as well as a high pressure compressor. The turbine maylikewise comprise a high pressure turbine and a low pressure turbine.

SUMMARY

An apparatus is provided comprising a radially inward segment portion, aradially outward segment portion, and a radially outward perforatedstructure coupled to the radially outward segment portion.

BRIEF DESCRIPTION OF THE DRAWINGS

The subject matter of the present disclosure is particularly pointed outand distinctly claimed in the concluding portion of the specification. Amore complete understanding of the present disclosure, however, may bestbe obtained by referring to the detailed description and claims whenconsidered in connection with the drawing figures, wherein like numeralsdenote like elements.

FIG. 1 illustrates, in accordance with various embodiments, a cutawayview of a jet engine;

FIG. 2 illustrates, in accordance with various embodiments, across-sectional view of portion of a jet engine turbine;

FIG. 3 illustrates, in accordance with various embodiments, a cutawayview of a MTF;

FIG. 4 illustrates, in accordance with various embodiments, a cutawayview of an outer annular structure of an MTF;

FIG. 5 illustrates, in accordance with various embodiments, aperspective view of a portion of a seal;

FIG. 6 illustrates, in accordance with various embodiments, across-sectional view of an inner annular structure of an MTF;

FIG. 7 illustrates, in accordance with various embodiments, across-sectional view of an outer annular structure of an MTF, whereinair impinges on a perforated structure to flow through a channel, slot,and/or gutter to reach a duct; and

FIG. 8 illustrates, in accordance with various embodiments, an explodedview of a first segment.

DETAILED DESCRIPTION

The detailed description of exemplary embodiments herein makes referenceto the accompanying drawings, which show exemplary embodiments by way ofillustration and their best mode. While these exemplary embodiments aredescribed in sufficient detail to enable those skilled in the art topractice the inventions, it should be understood that other embodimentsmay be realized and that logical, chemical and mechanical changes may bemade without departing from the spirit and scope of the inventions.Thus, the detailed description herein is presented for purposes ofillustration only and not of limitation. For example, the steps recitedin any of the method or process descriptions may be executed in anyorder and are not necessarily limited to the order presented.Furthermore, any reference to singular includes plural embodiments, andany reference to more than one component or step may include a singularembodiment or step. Also, any reference to attached, fixed, connected orthe like may include permanent, removable, temporary, partial, fulland/or any other possible attachment option. Additionally, any referenceto without contact (or similar phrases) may also include reduced contactor minimal contact.

As used herein, “aft” refers to the direction associated with the tail(e.g., the back end) of an aircraft, or generally, to the direction ofexhaust of the gas turbine. As used herein, “forward” refers to thedirected associated with the nose (e.g., the front end) of an aircraft,or generally, to the direction of flight or motion. For example, withreference to FIG. 1, central axis A-A′ may be described as extendingfrom a forward position (A) to an aft position (A′).

A gas turbine engine may comprise a high pressure turbine and a lowpressure turbine. Hot gas from a combustion section of a gas turbineengine may flow into the high pressure turbine and the low pressureturbine, in that order, from forward to aft. The kinetic energy of thehot gas is captured by the high pressure turbine and the low pressureturbine and converted into more other useful forms of energy. Highpressure turbines tend to operate at maximum efficiency when the gas ishot and the high pressure turbine is small. Low pressure turbines tendto work at maximum efficiency when the hot gases operate at the lowpressure turbine's largest diameter. Thus, for improved efficiency,there may be a large difference in the diameter between a high pressureturbine and a low pressure turbine. Conventionally, the forward stagesof the low pressure turbine were not as efficient as they could be.However, by using or coupling a mid-turbine frame between the highpressure turbine and the low pressure turbine, the hot gases may rapidlyexpand as they exit the high pressure turbine to gain a large diameterupon entry into the forward stages of the low pressure turbine. Forfurther information, U.S. Provisional Patent Application Ser. No.61/925,001 is hereby incorporated by reference in its entirety.

A mid-turbine frame may thus be disposed between a high pressure turbineand a low pressure turbine. As hot gases leave the high pressureturbine, heat may be transferred to the mid-turbine frame, or, morespecifically, the components that make up the mid-turbine frame. Certainstructures of the mid-turbine frame may be designed to thermally and/ormechanically protect high temperature intolerant components, such as,for example, support struts, air and oil service lines, and the like.Though various structural configurations and material selection mayenhance the thermal and/or mechanical protection, it may also beadvantageous to allow cooler air from other gas turbine engine locationsto enter a mid-turbine frame and cool (i.e., transfer heat away from)the mid-turbine frame. In various embodiments, cooling air is conductedinto one or more vanes to cool one or more high temperature intolerantcomponents and/or one or more vanes. Cooling air flow, however, isadvantageously be modulated. Thus, the incorporation of specializedstructures in a mid-turbine frame may be beneficial to cooling.

With reference now to FIG. 1, gas turbine engines (e.g., jet engines)100 may extend from forward to aft along a central axis A-A′. Asdescribed above, gas turbine engines 100 generally include a compressorto pressurize inflowing air, a combustor to burn a fuel in the presenceof the pressurized air, and a turbine to extract energy from theresulting combustion gases. The compressor may be divided into twosections. Specifically, the compressor may comprise a low pressurecompressor 102 situated forward of a high pressure compressor 104. Theturbine may likewise be divided into two sections. These include a highpressure turbine (or “HPT”) 106 situated forward of a low pressureturbine (or “LPT”) 108. The combustor 110 may be disposed axially aft ofthe HPT 106 and axially forward of the LPT 108.

In various embodiments, a structure, which may be referred to herein asa “mid-turbine frame” or “MTF” 112 may be included as part of the gasturbine engine 100. More particularly, as shown with respect to FIG. 2,the MTF 112 may be disposed aft of the HPT 106 and forward of the LPT108. The MTF 112 may generally comprise a duct configured to convey(hot) combustion gasses from the HPT 106 to the LPT 108. The MTF 112 maythus comprise an annular and/or semi-annular duct configured, inparticular, to permit the expansion of hot gasses exiting the HPT 106into the LPT 108. The MTF 112 may enlarge in diameter as it extends fromforward to aft along the central axis A-A′.

With reference to FIG. 3, the MTF 112 may more particularly comprise aplurality of segments (e.g., to illustrate a portion of an MTF 112, afirst segment 302 and second segment 304) that together form an MTF 112.For example, and again, to illustrate a portion of an MTF 112, the firstsegment 302 and the second segment 304 may comprise radially outerarcing surfaces and radially inner arcing surfaces that may be joined orsealed, as described herein, to form an outer annular structure 306 andan inner annular structure 308 of an MTF 112. Stated another way, firstsegment 302 and second segment 304 comprise arc segments that, whencoupled, form outer annular structure 306 and inner annular structure308, wherein outer annular structure 306 is radially farther fromcentral axis A-A′ than inner annular structure 308. Specifically, thefirst segment 302 may comprise an outer arcing surface 330 a and aninner arcing surface 330 b, while the second segment 304 may comprise anouter arcing surface 332 a and an inner arcing surface 332 b. The innerannular structure 308 may be situated radially inward of the outerannular structure 306, where the radially inward indicates closerproximity to central axis A-A′.

The MTF 112 may further comprise a plurality of vanes (e.g., 310 a and310 b) that extend radially outward from the inner annular structure 308toward the outer annular structure 306. Each vane may comprise a channelthat houses a variety of components (e.g., support struts, hydraulic andelectrical equipment, and the like). In various embodiments, any numberof vanes may be used in the construction of an MTF 112 (e.g., 9 vanes,18 vanes, and the like).

It may be understood that in a gas turbine engine, various componentsare supported by support structures such as support struts and the like.Moreover, air and oil service lines may be along the radius of centralaxis A-A′ to serve various radially inward components. However, as MTF112 is situated aft of HPT 106 and is configured to receive hot gasesfrom HPT 106, support struts, air and oil service lines, and the likewould be impaired or destroyed by hot gases from HPT 106. In variousembodiments, hot gases from HPT 106 are above 900° F. Accordingly, aplurality of vanes (e.g., 310 a and 310 b) may be configured to bothshield high temperature intolerant components from hot gases while alsoimposing minimal or near minimal aerodynamic resistance.

In various embodiments, each of the segments (e.g., 302 and 304)comprising the outer annular structure 306 and/or the inner annularstructure 308 may comprise a plurality of channels (e.g., 314 a, 314 b,314 c, 314 d, 316 a, 316 b, 316 c, 316 d) that extend axially along anaxial length each of the segments.

Each segment (e.g., 302 and 304) comprising the outer annular structure306 and the inner annular structure 308 may include a plurality oftenons that define axial terminuses of each segment 302 and 304. Forexample, the first segment 302 may include a first and second tenon(e.g., 318 a and 318 b) that define a first and second outer axialterminus of the first segment 302 and a third and fourth tenon (e.g.,318 c and 318 d) that define a third and fourth inner axial terminus ofthe first segment 302.

The same may be true with respect to the second segment 304. Forexample, the second segment 304 may include a first and second tenon(e.g., 320 a and 320 b) that define a first and second outer axialterminus of the second segment 304. Likewise, the second segment 304 mayinclude a third and fourth tenon (e.g., 320 c and 320 d) that define athird and fourth inner axial terminus of the second segment.

In various embodiments, each segment (e.g., 302 and 304) comprising theMTF 112 may be coupled to an adjacent segment by a seal 312 and/or 322.For example, with reference to FIG. 4, the second tenon 318 b of thefirst segment 302 may be coupled by the seal 312 to the first tenon 320a of the second segment 304. The seal 312 may thus couple or clamp thefirst segment 302 to the second segment 304 to form the outer annularstructure 306.

The seal 322 may similarly couple or clamp the fourth tenon 318 d of thefirst segment 302 to the third tenon 320 c of the second segment 304.Thus, a plurality of seals (e.g., 312 and 322) may couple a plurality ofsegments (both with respect to their respective inner annular structuresand outer annular structures) to form a substantially annular duct orMTF 112.

A seal 312 (see, e.g., FIG. 4) may comprise a first (male) member 402and a second (female) member 404. In various embodiments, the firstmember 402 may comprise a plurality of substantially “T-shaped”elements, for example, element 502 and element 504 (with brief referenceto FIG. 5), arranged and coupled axially along an axial member or body506 (as shown with respect to FIG. 5) while the second member 404 maycomprise an axial member configured to receive each of the plurality ofthe elements (e.g., 502, 504, etc.) For example, as shown with respectto FIG. 4, a T-shaped element 502 may extend radially through the secondmember 404. Thus, in various embodiments, the second member 404 maycomprise a “T-shape” (or two back to back “L-shapes”) as well, where thesecond member 404 receives the first member 402.

With reference to FIG. 6, a seal 322 is shown coupling the fourth tenon318 d of the first segment 302 to the third tenon 320 c of the secondsegment 304. As discussed above, the seal 322 may comprise a first(male) member 602 and a second (female) member 604. In variousembodiments, the first member 602 may comprise a plurality ofsubstantially “T-shaped” elements (e.g., element 606 arranged andcoupled axially along an axial member or strut while the second member604 may comprise an axial member configured to receive each of theplurality of the elements (e.g., 606). For example, a T-shaped element606 may extend radially through the second member 604. In variousembodiments, the second member 604 may comprise a “T-shape” (or two backto back “L-shapes”) as well, where the second member 604 receives the anelement 606 of the first member 602. In various embodiments, elements502 and/or 504 and/or member 602 may be threaded, such that an element502 and/or 504 may, for example, be threaded onto member 602 in a nutand bolt like fashion.

With returning attention to FIG. 3, each of the outer annular structure306 and/or inner annular structure 308 may be overlaid by (and/orcoupled to, via, e.g., the seal 312 and/or 322) to a perforatedstructure 324 (as shown with respect to the outer annular structure306). The perforated structure 324 may comprise an arced surface thatconforms or substantially conforms to the arc of the inner and/or outerannular structures 306 and/or 308. The perforated structure may furthercomprise any of a variety of temperature resistant materials and/oralloys. For example, a perforated structure may comprise at least one ofnickel, stainless steel, and one or more other metal alloys such as anaustenitic nickel chromium alloy (as sold under the trademark INCONEL).Perforations of perforated structure 324 may be manufactured by anysuitable process. For example, perforated structure 324 may be forged orcast. In various embodiments, perforations in perforated structure 324may be drilled or otherwise machined.

In operation, it may be beneficial to cool the equipment, as describedabove, that passes through the vanes 310 a and 310 b. As described,these vanes may pass through the MTF 112 duct, through which combustiongasses may flow at high velocity and temperature. Thus, to maintain theintegrity of the components within the vanes, cooling may be required.

To achieve this result, cooling air may be pumped in from, for example,an outer portion of the MTF 112, such that it impinges on the perforatedstructure 324. As may be understood, cooling air may also be receivedfrom other locations of a gas turbine engine and/or a nacelle thatsurrounds the gas turbine engine. Cooling air that is under pressure mayimpinge perforated structure 324 and permeate through the variousperforations (due to a difference in pressure) to cool each of the firstsegment 302 and second segment 304 of the outer annular structure 306.

With reference to FIG. 7, as air impinges on the outer annular structure306, the air may be channeled through the channel 314 b (and/or 314 a,not shown). The air may be further transferred to the seal 312 by way ofa slot 702 formed in each of the first segment 302 and second segment304 of the outer annular structure 306. These channels 314 b (and/or 314a) may help to cool the seal 312 itself, and, in various embodiments,the air may pass through tortuous gutters 704 in the seal 312 to enterto the hot gas flow path within the duct of the MTF 112. In variousembodiments, the tortuous gutters 704 may be at least partially formedby a narrow passage that exists between the first male member 402 of theseal 312, the tenon 318 a, and the perforated structure 324, whichcollectively form a passage through which air may flow. Air may furtherpass through channels formed in the vanes 310 a and 310 b themselves(not shown) to reach the channels 314 c and 314 d. Air may be receivedby the seal 322 (not shown) through a variety of slots, as describedabove, such that it travels through tortuous gutters in the seal 322 toenter, again, the hot gas flow path of the duct of the MTF 112. Theperforations of perforated structure 324 and the tortuous gutters 704provide modulation of radially inward flowing cooling air.

With reference to FIG. 8, first segment 302 is shown. Perforatedstructure 324 is shown separated from first segment 302 proximateradially outward segment portion 804.

Perforated structure 802 is also shown apart from first segment 302proximate radially outward segment portion 804. During manufacture,perforated structure 324 and perforated structure 802 may be joined tofirst segment 302. In that regard, perforated structure 324 may beattached to a radially outward portion of first segment 302 andperforated structure 802 may be attached to a radially inward portion offirst segment 302. In that regard, both perforated structure 324 andperforated structure 802 may allow for cooling air to permeatetherethrough and provide cooling to, for example, vane 310 a.

Benefits, other advantages, and solutions to problems have beendescribed herein with regard to specific embodiments. Furthermore, theconnecting lines shown in the various figures contained herein areintended to represent exemplary functional relationships and/or physicalcouplings between the various elements. It should be noted that manyalternative or additional functional relationships or physicalconnections may be present in a practical system. However, the benefits,advantages, solutions to problems, and any elements that may cause anybenefit, advantage, or solution to occur or become more pronounced arenot to be construed as critical, required, or essential features orelements of the inventions. The scope of the inventions is accordinglyto be limited by nothing other than the appended claims, in whichreference to an element in the singular is not intended to mean “one andonly one” unless explicitly so stated, but rather “one or more.”Moreover, where a phrase similar to “at least one of A, B, or C” is usedin the claims, it is intended that the phrase be interpreted to meanthat A alone may be present in an embodiment, B alone may be present inan embodiment, C alone may be present in an embodiment, or that anycombination of the elements A, B and C may be present in a singleembodiment; for example, A and B, A and C, B and C, or A and B and C.Different cross-hatching is used throughout the figures to denotedifferent parts but not necessarily to denote the same or differentmaterials.

Systems, methods and apparatus are provided herein. In the detaileddescription herein, references to “one embodiment,” “an embodiment,” “anexample embodiment,” etc., indicate that the embodiment described mayinclude a particular feature, structure, or characteristic, but everyembodiment may not necessarily include the particular feature,structure, or characteristic. Moreover, such phrases are not necessarilyreferring to the same embodiment. Further, when a particular feature,structure, or characteristic is described in connection with anembodiment, it is submitted that it is within the knowledge of oneskilled in the art to affect such feature, structure, or characteristicin connection with other embodiments whether or not explicitlydescribed. After reading the description, it will be apparent to oneskilled in the relevant art(s) how to implement the disclosure inalternative embodiments.

Furthermore, no element, component, or method step in the presentdisclosure is intended to be dedicated to the public regardless ofwhether the element, component, or method step is explicitly recited inthe claims. No claim element herein is to be construed under theprovisions of 35 U.S.C. 112(f), unless the element is expressly recitedusing the phrase “means for.” As used herein, the terms “comprises,”“comprising,” or any other variation thereof, are intended to cover anon-exclusive inclusion, such that a process, method, article, orapparatus that comprises a list of elements does not include only thoseelements but may include other elements not expressly listed or inherentto such process, method, article, or apparatus.

What is claimed is:
 1. An apparatus comprising: a radially inwardsegment portion; a radially outward segment portion; and a radiallyoutward perforated structure coupled to the radially outward segmentportion.
 2. The apparatus of claim 1, wherein a vane extends from theradially inward segment portion to the radially outward segment portion.3. The apparatus of claim 2, further comprising a radially inwardperforated structure coupled to the radially inward segment portion. 4.The apparatus of claim 2, wherein the vane defines a channel.
 5. Theapparatus of claim 2, wherein the radially inward segment portion andthe radially outward segment portion comprise a segment.
 6. Theapparatus of claim 5, wherein the segment comprise a first tenon thatdefines a first axial terminus of the segment and a second tenon thatdefines a second axial terminus of the segment.
 7. The apparatus ofclaim 5, wherein the segment at least partially defines a hot gas pathbetween a high pressure turbine (“HPT”) and a high pressure turbine(“LPT”).
 8. The apparatus of claim 1, further comprising a slotproximate to a seal that clamps a second segment to the segment.
 9. Theapparatus of claim 8, wherein the slot is configured to relay coolingair through the seal and into a hot gas path.
 10. The apparatus of claim9, further comprising a tortuous gutter.
 11. The apparatus of claim 10,wherein the tortuous gutter comprises a narrow passage between the seal,a first tenon of the segment, and the perforated structure.
 12. Theapparatus of claim 1, wherein the radially outward perforated structurecomprises a temperature resistant alloy.